S 085-032
(11)
Disconnect and remove all the test equipment.
S 435-033
(12)
Connect the electrical connectors to the autopilot actuators.
S 415-034
(13)
Install the tail cone access panel, 3802R (AMM 12-31-41/201).
G. Autopilot Elevator Actuator Verification
S 835-074
(1) Do the elevator rigging test in this task: "Rigging Tests" (AMM 22-11-00/501 or AMM 22-11-01/501).
TASK 22-11-26-825-076
3. Autopilot Elevator Actuator Adjustment (DFCS BITE Test) (-912 and on)
______________________________________
A. References
(1) AMM 12-31-41/201, Body Section 48 Access Doors and Panels
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737-300/400/500MAINTENANCE MANUAL
(2)
AMM 22-11-00/501 or AMM 22-11-01/501, Digital Flight Control System
(3)
AMM 24-22-00/201, Manual Control
(4)
AMM 27-31-00/501, Elevator and Tab Control System
(5)
AMM 29-15-00/201, Hydraulic A, B, and Standby System
(6)
OHM 27-07-09
B. Access
(1)
Location Zone
704 Tail Cone
(2)
Access Panel
3802 Tail Cone Access Door
C. Autopilot Elevator Actuator Adjustment
S 865-079
(1)
Do this task to fully adjust the elevator rigging before you can adjust the actuators: "Adjustment - Elevator and Tab Control System" (AMM 27-31-00/501).
S 015-046
(2)
Remove the tail cone access panel, 3802, to get access to the actuator (AMM 12-31-41/201).
S 035-065
(3)
Remove the bolt from one end of the rod assembly between the two actuator levers.
S 035-066
(4)
Remove the bolt from one end of the rod assembly between the actuator A lever and torque tube lever.
S 865-067
(5)
Put the actuators to the null position:
(a)
Do the preparation for the DFCS BITE test in this task: "Operational Test - Digital Flight Control System" (AMM 22-11-00/501 or AMM 22-11-01/501).
(b)
Push the INIT REF key on the CDU keyboard.
(c)
Push the LSK adjacent to <INDEX.
(d)
Push the LSK adjacent MAINT>.
(e)
Push the LSK adjacent to <DFCS.
(f)
Push the NEXT PAGE key on the CDU display.
(g)
Push the LSK adjacent to <RIGGING.
(h)
Do the Elevator Rigging Test (tests 51.00 thru 51.05) in this task: "Rigging Tests" (AMM 22-11-00/501 or AMM 22-11-01/501).
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(i) Make sure that the LVDT voltage on the CDU display is -2.00 |0.05v ac.
NOTE: Do not push the LSK adjacent to <CONTINUE or get out of
____ the BITE until the actuator adjustment is completed.
S 215-059
(6) Do a check on the shear rivets of the two output levers:
(a)
Examine the shear rivet areas.
(b)
Make sure that there is no movement in these areas.
(c)
If there is a movement, remove the lever assembly and replace the shear rivets (OHM 27-09-05).
S 435-055
(7) Install the rod assembly between the two actuator levers:
(a)
Adjust the rod assembly length until the bolt can go smoothly through the rod end and actuator lever.
(b)
Make sure that you can see the bearing threads of the rod end through the inspection hole in the rod assembly. Adjust the rod assembly if it is necessary.
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本文链接地址：737-300 400 500 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 2(10)
